摘要
对基于形状记忆合金(Shape memory alloy,SMA)丝驱动器的多关节变体机翼后缘模型,在指定飞行工况下结构的整体极限偏转角度是最重要的设计指标。本文根据SMA驱动器的力学本构模型,建立了在控制回复状态下的SMA-弹簧模型。基于N-S方程编制了2D流场求解器,并使用网格重构技术建立了后缘偏转时的多套流场网格,通过将后缘结构所受的气动载荷力矩对应施加于后缘结构的各个关节,在ANSYS静力分析模块中对后缘的偏转过程进行了数值仿真,考察了变体后缘的整体极限偏转角度。为验证仿真结果,对变体后缘结构进行了模拟加载实验。实验结果表明,本文使用的数值计算方法能够较为准确地预测变体后缘的整体极限偏转角度。
Mechanical analysis is implemented on a multi-joint morphing wing trailing edge actuated by the shape memory alloy（SMA）wire.Utilizing the mechanics constitutive model of the SMA wire,a SMA-spring model is established in the condition of recovering under control.Moreover,the fluid-structure coupling model of the morphing trailing edge is used to evaluate the mechanical and aerodynamic performances in prescribed flight conditions.Hence,a series of flow-field grids for the deflected trailing edge are built by the grid-reconstruction technology.Based on N-S equations,a flow-field solver is established to obtain the aerodynamic loads on envelops of morphing trailing edge.And then,the aerodynamic torque on every joint of trailing edge is calculated respectively,and with application of the ANSYS software,numerical simulations on the deflecting process of morphing trailing edge are performed.Through the above analysis,limit deflecting angles of the trailing edge are predicted.Finally,an experiment is carried out to verify the simulation results,and the experimental results show that the represented numerical method is feasible to predict the limit deflecting angles of morphing trailing edge accurately.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2015年第6期904-910,共7页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家自然科学基金(90716003)资助项目
十二五装备预研基金资助项目
江苏高校优势学科建设工程资助项目
关键词
测试计量技术及仪器
变体机翼后缘
形状记忆合金
N-S方程
力学分析
measurement technology and instruments
morphing wing trailing edge
shape memory alloy
N-S governing equation
mechanical analysis
